运载火箭静气动弹性流固耦合仿真研究  

Static Aeroelastic Analysis of Air-Launched Rocket Using Fluid-Structure Interaction Method

作　　者：完颜振海 刘佳佳 杨亮 孟超 WANYAN Zhen-hai;LIU Jia-jia;YANG Liang;MENG Chao(Beijing Institute of Astronautical System Engineering,Beijing 100076,China)

机构地区：[1]北京宇航系统工程研究所

出　　处：《计算机仿真》2019年第11期27-30,63,共5页Computer Simulation

摘　　要：细长体的运载火箭在大攻角飞行时可能承受较大的气动弯矩作用并会导致结构发生较大的弹性变形,需要开展流固耦合仿真以分析箭体表面压力分布和箭体弹性变形情况及其对结构安全性影响。将高精度的计算流体力学和计算结构力学耦合起来实现了一种静气动弹性分析方法,其中流体计算基于三维粘性Navier-Stokes方程求解,结构计算采用三维有限元静力学分析方法。在使用标准气弹机翼验证的基础上,采用上述方法对火箭超声速大攻角飞行时的箭体变形情况进行了研究,分析了不同壳体厚度对结构弹性变形的影响。结果表明基于上述方法能够开展精细化的静气弹分析,应用到细长体火箭上的分析结果为火箭的载荷与结构总体设计提供依据。Slender launch vehicle may bear significant high-attack aerodynamic moment and resultant large deformation of structure, hence coupled fluid-structure analysis is required for predicting the surface pressure, deformation of the rocket and its influence on safety of structure. A method for static aeroelastic analysis was realized based on high-accuracy CFD and CSD, with which the fluid simulation was adopting three-dimensional Navier-Stokes equation and the structural simulation was adopting three-dimensional static analysis. Compared analysis was conducted between this method and reduced-order structure model using standard AGARD wing, and then analyses of deformations of the supersonic air-launched rocket’s shell with different thicknesses were conducted. The results show that the given method can provide refined analyses for aeroelastic problems and the rocket’s analyses provide a basis for the load and structural design.

关 键 词：静气动弹性 流固交互 计算流体力学 计算结构力学 运载火箭 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]